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Rocket Design

DESIGN
The rocket body will be a cardboard tube with an outer diameter of 5.56 inches, and an internal diameter of 5.38 inches. The nose cone and fins will be purchased and fabricated, respectively. The overall height of the rocket is 93.68 inches. The rocket will contain the motor, electronics, ballast, main parachute, drogue parachute, and payload bays. The electronics bay will consist of hardware used for rocket location tracking. The ballast bay will hold weight located near the nosecone. The engine and payload bays will contain the motor assembly and payload, respectively.
MISSION PHASES
Phase 1: Launch and Ascent
The rocket launch, which includes the altimeter arming, rocket takeoff, and rocket ascent.
Phase 2: Apogee
During this phase, the altimeters will trigger the first set of black powder separation charges at apogee. Hereafter, the nose cone will separate from the rocket body and remain constrained by a tether.
Phase 3: Descent and Imaging
The third phase begins with the TRIPOD's ejection, drogue deployment, and primary system activation. In addition, the main rocket will also release its reefed main parachute. The two independent bodies will descend until reaching their main parachute deployment altitude. The rocket body and payload main parachutes will be released based upon altimeter readings. The TRIPOD will be taking and processing imaging during its descent.



Phase 4: Landing
The rocket and TRIPOD will reach the ground at a safe velocity via their parachutes. Once the TRIPOD has reached the ground, it will stand up. The ground station receiver will dictate where the rocket section and payload have landed based upon the data broadcasted by their tracking components.
RECOVERY
The rocket body altimeter electronics consist of two redundant circuits. Each circuit includes a Perfect Flight Strattologger CF barometric altimeter. The altimeters each have a dedicated battery and accessible arming switch. Each altimeter has an igniter connected the main parachute and the payload separation charges. One igniter from each altimeter is placed in the separation charges at either end of the electronics bay. Effectively, each separation charge contains two redundant igniters establishing a redundant recovery system.





TRACKING CIRCUIT
The rocket body tracking electronics are controlled with an Arduino Mega. The Arduino Mega is tasked with periodically collecting spatial data, packaging it, saving it, and forwarding the data to the transceiver. This is the only function off the Arduino Mega and it is executed in a continuous loop until the rocket body is found after landing and the circuit is powered off.
University of Cincinnati
© 2017 The University of Cincinnati – Baerocats Senior Design Team. 2850 Campus Way Baldwin 745 Cincinnati OH 45221. Email: patelcj@mail.uc.edu. Phone number: 614-620-4054